Aerothermodynamic transition tests on a model of the forward half of the Rockwell International Space Shuttle Orbiter Configuration 140C were conducted at Mach Number 8. Phase-change paint was used to determine the aerodynamic heating rates on the windward side of Orbiter models during simulated atmospheric reentry. The majority of the data was obtained using spherical trip elements of varying sizes at three different axial stations along the model to determine the effect of roughness size and location on boundary- layer transition. Additional data were taken with models which had scale indentations that simulated external tank attachment rings, nose wheel well doors, and a surface insulation interface gap. Data were taken over an angle-of-attack range from 20 to 40 deg at free-stream Reynolds numbers, based on the total Orbiter scaled length, from 3.2 to 16.1 million. Typical heat-transfer data were presented to illustrate boundary-layer transition locations and sensitivities to test variables.